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GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 500 AIRFOIL (goe500-il)
Reynolds number: 100,000
Max Cl/Cd: 65.62 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe500-il-100000-n5.txt
Download as CSV file: xf-goe500-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 500 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2282   0.09355   0.08859  -0.0633   0.9681   0.0450
  -8.000  -0.2166   0.08975   0.08478  -0.0675   0.9633   0.0466
  -7.750  -0.2121   0.08624   0.08128  -0.0701   0.9560   0.0469
  -7.500  -0.2039   0.08217   0.07721  -0.0742   0.9497   0.0468
  -7.250  -0.1981   0.07815   0.07320  -0.0776   0.9414   0.0469
  -7.000  -0.1846   0.07274   0.06777  -0.0849   0.9347   0.0482
  -6.750  -0.1765   0.06626   0.06126  -0.0932   0.9254   0.0494
  -6.500  -0.1522   0.05522   0.05006  -0.1097   0.9188   0.0500
  -6.250  -0.1272   0.04372   0.03818  -0.1256   0.9104   0.0516
  -6.000  -0.0982   0.04266   0.03705  -0.1278   0.9060   0.0538
  -5.750  -0.0522   0.03373   0.02718  -0.1414   0.9032   0.0562
  -5.500  -0.0099   0.02935   0.02194  -0.1478   0.9014   0.0594
  -5.250   0.0105   0.02752   0.01967  -0.1478   0.8933   0.0618
  -5.000   0.0439   0.02642   0.01842  -0.1495   0.8898   0.0639
  -4.750   0.0801   0.02519   0.01693  -0.1516   0.8874   0.0665
  -4.500   0.1062   0.02422   0.01571  -0.1517   0.8814   0.0694
  -4.250   0.1358   0.02335   0.01458  -0.1523   0.8763   0.0736
  -4.000   0.1699   0.02282   0.01401  -0.1536   0.8731   0.0787
  -3.750   0.2063   0.02195   0.01289  -0.1552   0.8708   0.0851
  -3.500   0.2259   0.02166   0.01262  -0.1539   0.8621   0.0900
  -3.250   0.2596   0.02108   0.01188  -0.1549   0.8585   0.1003
  -3.000   0.2958   0.02055   0.01124  -0.1564   0.8558   0.1139
  -2.750   0.3167   0.02026   0.01099  -0.1552   0.8462   0.1244
  -2.500   0.3526   0.01968   0.01037  -0.1565   0.8420   0.1395
  -2.250   0.3764   0.01943   0.01012  -0.1557   0.8329   0.1526
  -2.000   0.4099   0.01899   0.00966  -0.1565   0.8280   0.1684
  -1.750   0.4355   0.01879   0.00948  -0.1560   0.8203   0.1827
  -1.250   0.4976   0.01815   0.00888  -0.1568   0.8101   0.2187
  -1.000   0.5216   0.01804   0.00885  -0.1561   0.8017   0.2429
  -0.750   0.5546   0.01770   0.00856  -0.1567   0.7973   0.2782
  -0.500   0.5788   0.01766   0.00858  -0.1560   0.7888   0.3119
  -0.250   0.6107   0.01741   0.00838  -0.1565   0.7834   0.3522
   0.000   0.6374   0.01734   0.00838  -0.1561   0.7759   0.3893
   0.250   0.6674   0.01717   0.00827  -0.1562   0.7694   0.4289
   0.500   0.6959   0.01705   0.00823  -0.1561   0.7624   0.4680
   0.750   0.7242   0.01691   0.00819  -0.1560   0.7549   0.5142
   1.000   0.7527   0.01670   0.00815  -0.1558   0.7479   0.5807
   1.250   0.7784   0.01640   0.00813  -0.1550   0.7399   0.6785
   1.500   0.8055   0.01587   0.00795  -0.1543   0.7325   1.0000
   1.750   0.8341   0.01595   0.00793  -0.1542   0.7240   1.0000
   2.000   0.8622   0.01605   0.00795  -0.1541   0.7154   1.0000
   2.250   0.8919   0.01610   0.00792  -0.1542   0.7072   1.0000
   2.500   0.9182   0.01628   0.00806  -0.1538   0.6979   1.0000
   2.750   0.9489   0.01633   0.00804  -0.1541   0.6902   1.0000
   3.000   0.9735   0.01656   0.00826  -0.1534   0.6795   1.0000
   3.250   1.0013   0.01671   0.00839  -0.1533   0.6704   1.0000
   3.500   1.0286   0.01688   0.00854  -0.1530   0.6610   1.0000
   3.750   1.0539   0.01713   0.00880  -0.1525   0.6509   1.0000
   4.000   1.0823   0.01728   0.00894  -0.1524   0.6421   1.0000
   4.250   1.1067   0.01756   0.00925  -0.1517   0.6314   1.0000
   4.500   1.1322   0.01782   0.00954  -0.1512   0.6216   1.0000
   4.750   1.1598   0.01803   0.00976  -0.1509   0.6127   1.0000
   5.000   1.1829   0.01836   0.01015  -0.1501   0.6013   1.0000
   5.250   1.2069   0.01863   0.01046  -0.1492   0.5893   1.0000
   5.500   1.2307   0.01889   0.01073  -0.1483   0.5762   1.0000
   5.750   1.2550   0.01916   0.01104  -0.1475   0.5642   1.0000
   6.000   1.2782   0.01949   0.01144  -0.1466   0.5528   1.0000
   6.250   1.2997   0.01982   0.01182  -0.1453   0.5387   1.0000
   6.500   1.3202   0.02012   0.01211  -0.1438   0.5212   1.0000
   6.750   1.3369   0.02049   0.01251  -0.1417   0.4994   1.0000
   7.000   1.3529   0.02090   0.01285  -0.1394   0.4757   1.0000
   7.250   1.3673   0.02140   0.01334  -0.1370   0.4524   1.0000
   7.500   1.3809   0.02198   0.01385  -0.1345   0.4287   1.0000
   7.750   1.3924   0.02262   0.01449  -0.1317   0.4038   1.0000
   8.000   1.4014   0.02331   0.01519  -0.1286   0.3782   1.0000
   8.250   1.4087   0.02410   0.01598  -0.1253   0.3471   1.0000
   8.500   1.4123   0.02513   0.01689  -0.1216   0.3046   1.0000
   8.750   1.4081   0.02672   0.01814  -0.1173   0.2522   1.0000
   9.000   1.4019   0.02873   0.01981  -0.1131   0.2041   1.0000
   9.250   1.3954   0.03101   0.02178  -0.1093   0.1524   1.0000
   9.500   1.3886   0.03349   0.02397  -0.1058   0.1145   1.0000
   9.750   1.3855   0.03581   0.02617  -0.1029   0.0923   1.0000
  10.000   1.3846   0.03804   0.02838  -0.1004   0.0793   1.0000
  10.250   1.3852   0.04023   0.03060  -0.0981   0.0712   1.0000
  10.500   1.3837   0.04268   0.03306  -0.0960   0.0656   1.0000
  10.750   1.3859   0.04489   0.03540  -0.0942   0.0610   1.0000
  11.000   1.3860   0.04737   0.03796  -0.0926   0.0571   1.0000
  11.250   1.3826   0.05029   0.04090  -0.0909   0.0541   1.0000
  11.500   1.3853   0.05269   0.04348  -0.0896   0.0511   1.0000
  11.750   1.3868   0.05529   0.04621  -0.0884   0.0483   1.0000
  12.000   1.3868   0.05810   0.04910  -0.0874   0.0458   1.0000
  12.250   1.3855   0.06116   0.05220  -0.0863   0.0436   1.0000
  12.500   1.3907   0.06358   0.05480  -0.0853   0.0415   1.0000
  12.750   1.3952   0.06612   0.05748  -0.0845   0.0392   1.0000
  13.000   1.3990   0.06879   0.06022  -0.0838   0.0371   1.0000
  13.250   1.4028   0.07150   0.06293  -0.0830   0.0353   1.0000
  13.500   1.4110   0.07382   0.06539  -0.0821   0.0338   1.0000
  13.750   1.4181   0.07634   0.06812  -0.0814   0.0321   1.0000
  14.000   1.4235   0.07907   0.07101  -0.0809   0.0305   1.0000
  14.250   1.4277   0.08190   0.07396  -0.0806   0.0291   1.0000
  14.500   1.4331   0.08464   0.07673  -0.0803   0.0279   1.0000
  14.750   1.4398   0.08751   0.07975  -0.0798   0.0270   1.0000
  15.000   1.4416   0.09106   0.08361  -0.0797   0.0261   1.0000
  15.250   1.4410   0.09495   0.08778  -0.0799   0.0253   1.0000
  15.500   1.4384   0.09907   0.09216  -0.0805   0.0245   1.0000
  15.750   1.4341   0.10346   0.09677  -0.0815   0.0237   1.0000
  16.000   1.4292   0.10795   0.10146  -0.0828   0.0231   1.0000
  16.250   1.4242   0.11249   0.10618  -0.0843   0.0226   1.0000
  16.500   1.4191   0.11715   0.11099  -0.0861   0.0221   1.0000
  16.750   1.4145   0.12181   0.11579  -0.0879   0.0217   1.0000
  17.000   1.4090   0.12677   0.12092  -0.0900   0.0214   1.0000
  17.250   1.3963   0.13338   0.12777  -0.0934   0.0213   1.0000
  17.500   1.3808   0.14083   0.13549  -0.0978   0.0212   1.0000
  17.750   1.3645   0.14884   0.14372  -0.1028   0.0212   1.0000
  18.000   1.3470   0.15757   0.15268  -0.1086   0.0212   1.0000
  18.250   1.3289   0.16700   0.16232  -0.1151   0.0212   1.0000
  18.500   1.3094   0.17756   0.17306  -0.1226   0.0213   1.0000
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